Shock-tube technique developed by Grumman Aircraft Engineering Corp simulates exhaust plumes and their effects on vehicles in space environment; helium driver gas expands behind detonation wave that propagates through combustible driven gas; initial conditions in shock tube can be adjusted to produce steady, uniform flow region behind detonation wave; after wave reflects from end wall of tube, stagnant, burned gas flows through nozzle into test chamber; density and velocity distributions, enthalpy, chemical constituency, full-scale Reynolds number, and hard vacuum background pressure are simulated simultaneously; facility, prerun calculations, instrumentation, and some results. (11877)


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    Titel :

    Detonation tube technique for simulating rocket plumes in space environment


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Leng, J. (Autor:in) / Oman, R.A. (Autor:in) / Hopkins, H.B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1968


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :